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Image L70-1807 is available as an electronic file from the photo lab. See URL. -- Photographed on 02/09/70. -- Test subject sitting at the controls: Project LOLA or Lunar Orbit and Landing Approach was a simulator built at Langley to study problems related to landing on the lunar surface. It was a complex project that cost nearly $2 million dollars. James Hansen wrote: "This simulator was designed to provide a pilot with a detailed visual encounter with the lunar surface; the machine consisted primarily of a cockpit, a closed-circuit TV system, and four large murals or scale models representing portions of the lunar surface as seen from various altitudes. The pilot in the cockpit moved along a track past these murals which would accustom him to the visual cues for controlling a spacecraft in the vicinity of the moon. Unfortunately, such a simulation--although great fun and quite aesthetic--was not helpful because flight in lunar orbit posed no special problems other than the rendezvous with the LEM, which the device did not simulate. Not long after the end of Apollo, the expensive machine was dismantled." (p. 379) From Ellis J. White, "Discussion of Three Typical Langley Research Center Simulation Programs," Paper presented at the Eastern Simulation Council (EAI's Princeton Computation Center), Princeton, NJ, October 20, 1966. "A typical mission would start with the first cart positioned on model 1 for the translunar approach and orbit establishment. After starting the descent, the second cart is readied on model 2 and, at the proper time, when superposition occurs, the pilot's scene is switched from model 1 to model 2. then cart 1 is moved to and readied on model 3. The procedure continues until an altitude of 150 feet is obtained. The cabin of the LM vehicle has four windows which represent a 45 degree field of view. The projection screens in front of each window represent 65 degrees which allows limited head motion before the edges of the display can be seen. The lunar scene is presented to the pilot by rear projection on the screens with four Schmidt television projectors. The attitude orientation of the vehicle is represented by changing the lunar scene through the portholes determined by the scan pattern of four orthicons. The stars are front projected onto the upper three screens with a four-axis starfield generation (starball) mounted over the cabin and there is a separate starball for the low window. -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 379.

Images L63-2988 and L63-2989 are available as an electronic files from the photo lab. See URL. -- Photographed on 04/08/1963. -- Construction of the Lunar Landing Research Facility. James Hansen noted that "it was conceived in 1962 by engineer Donald Hewes and built under the careful direction of his quiet but ingenious division chief, W. Hewitt Phillips, this gigantic facility designed to develop techniques for landing the rocket-powered LEM on the moon's surface." (p. 373) A.W. Vigil wrote in his paper "Piloted Space-Flight Simulation at Langley Research Center," "Ground-based simulators are not very satisfactory for studying the problems associated with the final phases of landing. This is due primarily to the fact that the visual scene cannot be simulated with sufficient realism. For this reason it is preferable to go to some sort of flight-test simulator which can provide real-life visual cues. One research facility designed to study the final phases of lunar landing is in operation at Langley. ... The facility is an overhead crane structure about 250 feet tall and 400 feet long. The crane system supports five-sixths of the vehicle's weight through servo-driven vertical cables. The remaining one-sixth of the vehicle weight pulls the vehicle downward simulating the lunar gravitational force. During actual flights the overhead crane system is slaved to keep the cable near vertical at all times. A gimbal system on the vehicle permits angular freedom for pitch, roll, and yaw. The facility is capable of testing vehicles up to 20,000 pounds. A research vehicle, weighing 10,500 pounds fully loaded, is being used and is shown [in this picture]. This vehicle is provided with a large degree of flexibility in cockpit positions, instrumentation, and control parameters. It has main engines of 6,000 pounds thrust, throttle able down to 600 pounds, and attitude jets. This facility is studying the problems of the final 200 feet of lunar landing and the problems of maneuvering about in close proximity to the lunar surface." -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), pp. 373-378; A.W. Vigil, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966.

Apollo Soyuz Test Project ASTP, Soyuz -19, End View -Instrument Assembly, End-Range =10 meters. Image taken on Revolution 29, Greenwich Mean Time GMT Time of Photo 198:15:50, Ground Elapsed Time GET 44:00, Altitude 222 km. Original Film Magazine: CX-06,Laboratory Roll 1; Camera Data: Hasselbald Reflex, 70-mm, Model 500EL, NASA Modified; Film Data: 70-mm Ektachrome, MS, Type QX-807, ASA=64, 50mm Lens.

Apollo Soyuz Test Project ASTP, Soyuz -19, End View -Instrument Assembly, End-Range =10 meters. Image taken on Revolution 29, Greenwich Mean Time GMT Time of Photo 198:15:50, Ground Elapsed Time GET 44:00, Altitude 222 km. Original Film Magazine: CX-06,Laboratory Roll 1; Camera Data: Hasselbald Reflex, 70-mm, Model 500EL, NASA Modified; Film Data: 70-mm Ektachrome, MS, Type QX-807, ASA=64, 50mm Lens.

Apollo Soyuz Test Project ASTP, Soyuz -19, Top View, Range =9 Meters. Image taken on Revolution 29, Greenwich Mean Time GMT Time of Photo 198:16:00, Ground Elapsed Time GET 44:10, Altitude 222 km. Original Film Magazine: CX-06,Laboratory Roll 1; Camera Data: Hasselbald Reflex, 70-mm, Model 500EL, NASA Modified; Film Data: 70-mm Ektachrome, MS,Type QX-807, ASA=64, 50mm Lens.

Image L64-9970 is available as an electronic file from the photo lab. See URL. -- Photographed on 10/29/1964. -- Originally the Rendezvous was used by the astronauts preparing for Gemini missions. The Rendezvous Docking Simulator was then modified and used to develop docking techniques for the Apollo program. "The LEM pilot's compartment, with overhead window and the docking ring (idealized since the pilot cannot see it during the maneuvers), is shown docked with the full-scale Apollo Command Module." A.W. Vogeley described the simulator as follows: "The Rendezvous Docking Simulator and also the Lunar Landing Research Facility are both rather large moving-base simulators. It should be noted, however, that neither was built primarily because of its motion characteristics. The main reason they were built was to provide a realistic visual scene. A secondary reason was that they would provide correct angular motion cues (important in control of vehicle short-period motions) even though the linear acceleration cues would be incorrect." -- Published in A.W. Vogeley, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966;

Medical requirements for the future Crew Exploration Vehicle (CEV), Lunar Surface Access Module (LSAM), advanced Extravehicular Activity (EVA) suits and Lunar habitat are currently being developed. Crews returning to the lunar surface will construct the lunar habitat and conduct scientific research. Inherent in aggressive surface activities is the potential risk of injury to crewmembers. Physiological responses and the operational environment for short forays during the Apollo lunar missions were studied and documented. Little is known about the operational environment in which crews will live and work and the hardware will be used for long-duration lunar surface operations. Additional information is needed regarding productivity and the events that affect crew function such as a compressed timeline. The Space Medicine Division at the NASA Johnson Space Center (JSC) requested a study in December 2005 to identify Apollo mission issues relevant to medical operations that had impact to crew health and/or performance. The operationally oriented goals of this project were to develop or modify medical requirements for new exploration vehicles and habitats, create a centralized database for future access, and share relevant Apollo information with the multiple entities at NASA and abroad participating in the exploration effort.

Test systems are developed for rendezvous and docking of manned spacecraft and stations that are suitable for use as a standard international system. This includes the rendezvous and docking of Apollo and Soyuz spacecraft, and crew transfer. The conduct of the mission will include: (1) testing of compatible rendezvous systems in orbit; (2) testing of universal docking assemblies; (3) verifying the techniques for transfer of cosmonauts and astronauts; (4) performing certain activities by U.S.A. and U.S.S.R. crews in joint flight; and (5) gaining of experience in conducting joint flights by U.S.A. and U.S.S.R. spacecraft, including, in case of necessity, rendering aid in emergency situations.

Astronaut Allen Bean with Lunar Landing Research Facility (LLRF) crew.

Photographed on 05/16/1966. -- OMEGA (One-Man Extravehicular Gimbal Arrangement) shown here permits unlimited freedom, and was designed around a parallel pair of 32-inch-diameter thin-line angular-contact bearings with half the balls removed to minimize friction. Tests have been conducted with OMEGA subjects in flight suits and pressure suits to determine the best gimbal restraint system and operation techniques. A.W. Vogeley described OMEGA as follows: "As mentioned previously, Langley is conducting in-house and contract studies of extra-vehicular activities wherein zero gravity is simulated by the water-immersion technique. ... Water immersion is a very useful technique where motions are slow. When more rapid motion is required, as in studying one-man propulsion systems, other approaches are required. For these studies Langley has been using the RDS [Rendezvous Docking Simulator] in a manner similar to the LLRF [Lunar Landing Research Facility] technique. The test subjects are suspended in a sling support from a single RDS cable. As they translate about, the RDS tracks them, keeping the cable vertical. The test subjects operate in an effectively zero g environment in the horizontal plane. Tracking was originally done visually using closed-circuit TV, but recently a fast-response servo system using cable angle sensors has provided better operation. ... Some results of tests where subjects moved about merely by jumping and also where propulsion in the form of simple "jet-shoes" was provided are given in reference 20. Both methods, within limits, appear feasible. Full six-degree-of-freedom equipment for studies of more sophisticated one-man propulsion systems is now being procured. Called OMPRA (One-Man Propulsion Research Apparatus), the device will provide a gimbal system for rotational freedom, a quick response vertical servo for this translational freedom that is not now feasible with the RDS, and a versatile maneuvering unit." -- Published in A.W. Vogeley, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966.

Images L67-1853 and L67-1855 are available as electronic files from the photo lab. See URL. -- Photographed on 02/05/67. -- Liftoff of Lunar Orbiter III from Complex 13.

Images L67-1853 and L67-1855 are available as electronic files from the photo lab. See URL. -- Photographed on 02/05/67. -- Liftoff of Lunar Orbiter III from Complex 13.

Forty years ago on July 15, 1975, a Russian Soyuz spacecraft and an American Apollo spacecraft lifted off from their respective launch sites in Baikonur, Kazakhstan, and the Kennedy Space Center in Florida to send cosmonauts Alexey Leonov and Valery Kubasov and astronauts Tom Stafford, Vance Brand and Deke Slayton on a landmark mission to linkup their vehicles for the first time. The historic docking occurred on July 17, 1975, in what many consider the pinnacle moment of a flight that opened the door to international cooperation between the two countries and the birth of the International Space Station. The video includes interviews conducted in Moscow with Soyuz Commander Alexey Leonov in May 2014, and with Apollo Commander Tom Stafford conducted in Houston in June 2015, as well as highlights of the mission itself.

A prelaunch press conference shows the crewmembers of Apollo 11, Commander Neil A. Armstrong, Lunar Module Pilot Edwin E. Aldrin, Jr., and Command Module Pilot Michael Collins, answering questions about their upcoming mission this section has sound, the rest of the video is without sound. Footage is seen of the crew during training for the extravehicular activity portion of the mission and using the flight simulator.

Researcher checks model of Project Fire Reentry package to be tested in Unitary Plan Wind Tunnel. Project FIRE (Flight Investigation Reentry Environment) studied the effects of reentry heating on spacecraft materials. It involved both wind tunnel and flight tests, although the majority were tests with Atlas rockets and recoverable reentry packages. These flight tests took place at Cape Canaveral in Florida. Wind tunnel tests were made in several Langley tunnels including the Unitary Plan Wind Tunnel, the 8-foot High-Temperature Tunnel and the 9x6-Foot Thermal Structures Tunnel.

This illustration depicts a configuration of the Soyuz spacecraft for the Apollo-Soyuz Test Project (ASTP). The ASTP was the first international docking of the U.S.'s Apollo spacecraft and the U.S.S.R.'s Soyuz spacecraft in space. For this project, the Soviets built another in their continuing series of Soyuz space capsules. The U.S. used the Saturn IB Apollo capsule. A joint engineering team from the two countries met to develop a docking system that permitted the two spacecraft to link in space and allowed the crews to travel from one spacecraft to the other.

Langley Center Director Floyd Thompson shows Ann Kilgore the "picture of the century." This was the first picture of the earth taken from space. From Spaceflight Revolution: "On 23 August 1966 just as Lunar Orbiter I was about to pass behind the moon, mission controllers executed the necessary maneuvers to point the camera away from the lunar surface and toward the earth. The result was the world's first view of the earth from space. It was called "the picture of the century' and "the greatest shot taken since the invention of photography." Not even the color photos of the earth taken during the Apollo missions superseded the impact of this first image of our planet as a little island of life floating in the black and infinite sea of space." Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), pp. 345-346.

Test subject sitting at the controls: Project LOLA or Lunar Orbit and Landing Approach was a simulator built at Langley to study problems related to landing on the lunar surface. It was a complex project that cost nearly $2 million dollars. James Hansen wrote: "This simulator was designed to provide a pilot with a detailed visual encounter with the lunar surface; the machine consisted primarily of a cockpit, a closed-circuit TV system, and four large murals or scale models representing portions of the lunar surface as seen from various altitudes. The pilot in the cockpit moved along a track past these murals which would accustom him to the visual cues for controlling a spacecraft in the vicinity of the moon. Unfortunately, such a simulation--although great fun and quite aesthetic--was not helpful because flight in lunar orbit posed no special problems other than the rendezvous with the LEM, which the device did not simulate. Not long after the end of Apollo, the expensive machine was dismantled." (p. 379) From Ellis J. White, "Discussion of Three Typical Langley Research Center Simulation Programs," Paper presented at the Eastern Simulation Council (EAI's Princeton Computation Center), Princeton, NJ, October 20, 1966. "A typical mission would start with the first cart positioned on model 1 for the translunar approach and orbit establishment. After starting the descent, the second cart is readied on model 2 and, at the proper time, when superposition occurs, the pilot's scene is switched from model 1 to model 2. then cart 1 is moved to and readied on model 3. The procedure continues until an altitude of 150 feet is obtained. The cabin of the LM vehicle has four windows which represent a 45 degree field of view. The projection screens in front of each window represent 65 degrees which allows limited head motion before the edges of the display can be seen. The lunar scene is presented to the pilot by rear projection on the screens with four Schmidt television projectors. The attitude orientation of the vehicle is represented by changing the lunar scene through the portholes determined by the scan pattern of four orthicons. The stars are front projected onto the upper three screens with a four-axis starfield generation (starball) mounted over the cabin and there is a separate starball for the low window. Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 379.

The laboratory controls to be used within the photographic technology division (PTD) for processing original space flight films exposed on the Apollo Soyuz Test Project mission are specified. The sensitometric exposures to be used by PTD for certifying processes, for exposing Houston Controls, and for preflight and postflight exposures on original films as well as procedures for film certification are described. Processing conditions used to achieve each control and processing machine operating parameters are included.

Analysis of lunar landing point designator operation

Determining test requirements for LM landing radar for F mission

Effect of cabin pressure on environmental control system

Construction of the Lunar Landing Research Facility. James Hansen noted that "it was conceived in 1962 by engineer Donald Hewes and built under the careful direction of his quiet but ingenious division chief, W. Hewitt Phillips, this gigantic facility designed to develop techniques for landing the rocket-powered LEM on the moon's surface." (p. 373) A.W. Vigil wrote in his paper "Piloted Space-Flight Simulation at Langley Research Center," "Ground-based simulators are not very satisfactory for studying the problems associated with the final phases of landing. This is due primarily to the fact that the visual scene cannot be simulated with sufficient realism. For this reason it is preferable to go to some sort of flight-test simulator which can provide real-life visual cues. One research facility designed to study the final phases of lunar landing is in operation at Langley. ... The facility is an overhead crane structure about 250 feet tall and 400 feet long. The crane system supports five-sixths of the vehicle's weight through servo-driven vertical cables. The remaining one-sixth of the vehicle weight pulls the vehicle downward simulating the lunar gravitational force. During actual flights the overhead crane system is slaved to keep the cable near vertical at all times. A gimbal system on the vehicle permits angular freedom for pitch, roll, and yaw. The facility is capable of testing vehicles up to 20,000 pounds. A research vehicle, weighing 10,500 pounds fully loaded, is being used and is shown [in this picture]. This vehicle is provided with a large degree of flexibility in cockpit positions, instrumentation, and control parameters. It has main engines of 6,000 pounds thrust, throttle able down to 600 pounds, and attitude jets. This facility is studying the problems of the final 200 feet of lunar landing and the problems of maneuvering about in close proximity to the lunar surface." Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), pp. 373-378; A.W. Vigil, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966.

Agena Docking Simulator Target.

OMEGA (One-Man Extravehicular Gimbal Arrangement) shown here permits unlimited freedom, and was designed around a parallel pair of 32-inch-diameter thin-line angular-contact bearings with half the balls removed to minimize friction. Tests have been conducted with OMEGA subjects in flight suits and pressure suits to determine the best gimbal restraint system and operation techniques. A.W. Vogeley described OMEGA as follows: "As mentioned previously, Langley is conducting in-house and contract studies of extra-vehicular activities wherein zero gravity is simulated by the water-immersion technique. ... Water immersion is a very useful technique where motions are slow. When more rapid motion is required, as in studying one-man propulsion systems, other approaches are required. For these studies Langley has been using the RDS [Rendezvous Docking Simulator] in a manner similar to the LLRF [Lunar Landing Research Facility] technique. The test subjects are suspended in a sling support from a single RDS cable. As they translate about, the RDS tracks them, keeping the cable vertical. The test subjects operate in an effectively zero g environment in the horizontal plane. Tracking was originally done visually using closed-circuit TV, but recently a fast-response servo system using cable angle sensors has provided better operation. ... Some results of tests where subjects moved about merely by jumping and also where propulsion in the form of simple "jet-shoes" was provided are given in reference 20. Both methods, within limits, appear feasible. Full six-degree-of-freedom equipment for studies of more sophisticated one-man propulsion systems is now being procured. Called OMPRA (One-Man Propulsion Research Apparatus), the device will provide a gimbal system for rotational freedom, a quick response vertical servo for this translational freedom that is not now feasible with the RDS, and a versatile maneuvering unit." Published in A.W. Vogeley, "Piloted Space-Flight Simulation at Langley Research Center," Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966.

Image L66-9457 is available as an electronic file from the photo lab. See URL. -- Photographed on 11/08/66. -- Liftoff of Lunar Orbiter B from Complex 3.

Lunar orbit insertion abort procedures for hybrid lunar missions

Image L62-425 is available as an electronic file from the photo lab. See URL. -- Photographed on 01/15/1963. -- Construction of Model 2 used in the LOLA simulator: Project LOLA or Lunar Orbit and Landing Approach was a simulator built at Langley to study problems related to landing on the lunar surface. It was a complex project that cost nearly $2 million dollars. James Hansen wrote: "This simulator was designed to provide a pilot with a detailed visual encounter with the lunar surface; the machine consisted primarily of a cockpit, a closed-circuit TV system, and four large murals or scale models representing portions of the lunar surface as seen from various altitudes. The pilot in the cockpit moved along a track past these murals which would accustom him to the visual cues for controlling a spacecraft in the vicinity of the moon. Unfortunately, such a simulation--although great fun and quite aesthetic--was not helpful because flight in lunar orbit posed no special problems other than the rendezvous with the LEM, which the device did not simulate. Not long after the end of Apollo, the expensive machine was dismantled." (p. 379) Ellis J. White wrote in his paper, "Discussion of Three Typical Langley Research Center Simulation Programs," "Model 1 is a 20-foot-diameter sphere mounted on a rotating base and is scaled 1 in. = 9 miles. Models 2,3, and 4 are approximately 15x40 feet scaled sections of model 1. Model 4 is a scaled-up section of the Crater Alphonsus and the scale is 1 in. = 200 feet. All models are in full relief except the sphere." -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, NASA SP-4308, p. 379; Ellis J. White, "Discussion of Three Typical Langley Research Center Simulation Programs," Paper presented at the Eastern Simulation Council (EAI's Princeton Computation Center), Princeton, NJ, October 20, 1966.

Computerized performance evaluation of Apollo thrust vector digital autopilot control system

Lunar landmark sighting techniques for Apollo command service module

FM degradation by multipath in closed chamber

To avoid the possibility of an unnecessary launch delay, a special program was initiated to provide aircraft measurement of electric fields at various altitudes over the Apollo vehicle launch pad. Eight aircraft, each equipped with electric field meters, were used in the program. This program and some of the more important findings are discussed. Also included is a summary of the history of manned space vehicle involvement with lightning, a brief description of the lightning instrumentation in use at KSC (Kennedy Space Center) at the time of the Apollo Soyuz mission and a discussion of the airborne instrumentation and related data.

Apollo Soyuz Test Project ASTP, Soyuz-19, Docking End, Range = 23 Meters. Image taken on Revolution 57. Greenwich Mean Time GMT of Photo 200:12:31, Ground Elapsed Time GET 88:41. Altitude 222 km. Original Film Magazine: CX-11, Laboratory Roll 9; Camera Data: Hasselblad Reflex,70-mm, Module 500EL, NASA Modified; Film Data: 70-mm Ektachrome EF,Type QX-807, ASA=64 Laboratory Adjusted, 50mm Lens

Preliminary data are documented for a typical launch window opening, a typical in-plane case, and a typical launch window closing trajectory, not necessarily in the same daily launch window, for the Apollo Soyuz test project mission. The Soyuz will be launched first and the Apollo will be launched on the first opportunity, 7 hours 21 minutes later. If the Apollo is unable to be launched on the first opportunity, four additional opportunities are available at 30 hours 56 minutes, 54 hours 31 minutes, 78 hours 05 minutes, and 101 hours 40 minutes. If the Apollo cannot be launched in this time frame, no further attempt will be made to launch and rendezvous with the first Soyuz. Soyuz will then be deorbited; however, a second Soyuz was made available for the same purposes.

Image L64-8154 is available as an electronic file from the photo lab. See URL. -- Photographed on 08/31/1964. -- Artist rendering of the Lunar Orbiter Project. -- Published in James R. Hansen, Spaceflight Revolution, NASA SP-4308, Chapter 10, "To Behold the Moon: The Lunar Orbiter Project."

CSM-active rendezvous simulation studies using sextant and ranging device

The lunar module design underwent gradual evolution from the first configuration proposed by Grumman in 1962. This model is the 1964 version. Langley had the task of building a simulator for the astronauts to practice lunar landings. The configuration of the initial vehicle used with the Lunar Landing Research Facility (LLRF) was changed in 1967 to more accurately reflect the standing position of the astronauts, cockpit arrangement, instrumentation, controls and field of view.

Experiments proposed for the Apollo-Soyuz space mission are discussed. Data focus of space processing and manufacturing, earth surveys, and life sciences. Special efforts were made to test the compatibility of the rendezvous and docking systems for manned spacecraft. Mission planning programs, personnel training, and spacecraft modifications for both spacecraft are included.

Project LOLA. Test subject sitting at the controls: Project LOLA or Lunar Orbit and Landing Approach was a simulator built at Langley to study problems related to landing on the lunar surface. It was a complex project that cost nearly $2 million dollars. James Hansen wrote: "This simulator was designed to provide a pilot with a detailed visual encounter with the lunar surface; the machine consisted primarily of a cockpit, a closed-circuit TV system, and four large murals or scale models representing portions of the lunar surface as seen from various altitudes. The pilot in the cockpit moved along a track past these murals which would accustom him to the visual cues for controlling a spacecraft in the vicinity of the moon. Unfortunately, such a simulation--although great fun and quite aesthetic--was not helpful because flight in lunar orbit posed no special problems other than the rendezvous with the LEM, which the device did not simulate. Not long after the end of Apollo, the expensive machine was dismantled." (p. 379) Ellis J. White wrote in his paper, "Discussion of Three Typical Langley Research Center Simulation Programs" : "A typical mission would start with the first cart positioned on model 1 for the translunar approach and orbit establishment. After starting the descent, the second cart is readied on model 2 and, at the proper time, when superposition occurs, the pilot's scene is switched from model 1 to model 2. then cart 1 is moved to and readied on model 3. The procedure continues until an altitude of 150 feet is obtained. The cabin of the LM vehicle has four windows which represent a 45 degree field of view. The projection screens in front of each window represent 65 degrees which allows limited head motion before the edges of the display can be seen. The lunar scene is presented to the pilot by rear projection on the screens with four Schmidt television projectors. The attitude orientation of the vehicle is represented by changing the lunar scene through the portholes determined by the scan pattern of four orthicons. The stars are front projected onto the upper three screens with a four-axis starfield generation (starball) mounted over the cabin and there is a separate starball for the low window.

The electrophoresis of six columns was accomplished on the Apollo-Soyuz test Project. After separation, these columns were frozen in orbit and were returned for ground-based analyses. One major goal of the MA-011 experiment was the assessment of the separation achieved in orbit by slicing these frozen columns. The slicing of the frozen columns required a new device. The development of that device is described.

Requirements for antennas, radio and terminal equipment aboard Apollo communication and tracking ships to communicate with land stations by satellite relay

Apollo project - data analysis of daily peak surface wind at Cape Kennedy

Artists used paintbrushes and airbrushes to recreate the lunar surface on each of the four models comprising the LOLA simulator. Project LOLA or Lunar Orbit and Landing Approach was a simulator built at Langley to study problems related to landing on the lunar surface. It was a complex project that cost nearly $2 million dollars. James Hansen wrote: "This simulator was designed to provide a pilot with a detailed visual encounter with the lunar surface; the machine consisted primarily of a cockpit, a closed-circuit TV system, and four large murals or scale models representing portions of the lunar surface as seen from various altitudes. The pilot in the cockpit moved along a track past these murals which would accustom him to the visual cues for controlling a spacecraft in the vicinity of the moon. Unfortunately, such a simulation--although great fun and quite aesthetic--was not helpful because flight in lunar orbit posed no special problems other than the rendezvous with the LEM, which the device did not simulate. Not long after the end of Apollo, the expensive machine was dismantled." (p. 379) Ellis J. White further described LOLA in his paper "Discussion of Three Typical Langley Research Center Simulation Programs," "Model 1 is a 20-foot-diameter sphere mounted on a rotating base and is scaled 1 in. = 9 miles. Models 2,3, and 4 are approximately 15x40 feet scaled sections of model 1. Model 4 is a scaled-up section of the Crater Alphonsus and the scale is 1 in. = 200 feet. All models are in full relief except the sphere." Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 379; From Ellis J. White, "Discussion of Three Typical Langley Research Center Simulation Programs," Paper presented at the Eastern Simulation Council (EAI's Princeton Computation Center), Princeton, NJ, October 20, 1966.

Lunar module navigation systems accuracies for powered descent, ascent, and abort trajectories

Proceedings of an Oral History Workshop Conducted July 21, 1989 Moderator: John M. Logsdon Participants: Howard W. Tindall George E. Mueller Owen W. Morris Maxime A. Faget Robert A. Gilruth Christopher C. Kraft Monographs In Aerospace History, No. 14

Image L65-3485 is available as an electronic file from the photo lab. See URL. -- Photographed on 05/05/1965. -- Special "space" suit for the Reduced Gravity Walking Simulator located at the Lunar Landing Facility. The purpose of this simulator was to study the subject while walking, jumping or running. Researchers conducted studies of various factors such as fatigue limit, energy expenditure, and speed of locomotion. A.W. Vigil described the purpose of the simulator in his paper "Discussion of Existing and Planned Simulators for Space Research," "When the astronauts land on the moon they will be in an unfamiliar environment involving, particularly, a gravitational field only one-sixth as strong as on earth. A novel method of simulating lunar gravity has been developed and is supported by a puppet-type suspension system at the end of a long pendulum. A floor is provided at the proper angle so that one-sixth of the subject's weight is supported by the floor with the remainder being supported by the suspension system. This simulator allows almost complete freedom in vertical translation and pitch and is considered to be a very realistic simulation of the lunar walking problem. For this problem this simulator suffers only slightly from the restrictions in lateral movement it puts on the test subject. This is not considered a strong disadvantage for ordinary walking problems since most of the motions do, in fact, occur in the vertical plane. However, this simulation technique would be severely restrictive if applied to the study of the extra-vehicular locomotion problem, for example, because in this situation complete six degrees of freedom are rather necessary. This technique, in effect, automatically introduces a two-axis attitude stabilization system into the problem. The technique could, however, be used in preliminary studies of extra-vehicular locomotion where, for example, it might be assumed that one axis of the attitude control system on the astronaut maneuvering unit may have failed." -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 377; A.W. Vigil, "Discussion of Existing and Planned Simulators for Space Research," Paper presented at Conference on the Role of Simulation in Space Technology," Blacksburg, VA, August 17-21, 1964.

Image L65-8009 is available as an electronic file from the photo lab. See URL. -- Photographed on 10/29/1965. -- 1/4 scale model of Apollo Heat Shield being prepared for testing. -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, (Washington: NASA, 1995), p. 356.

Video for the song "Apollo" by Mercury Project

Project FIRE (Flight Investigation Reentry Environment) studied the effects of reentry heating on spacecraft materials. It involved both wind tunnel and flight tests, although the majority were tests with Atlas rockets and recoverable reentry packages. These flight tests took place at Cape Canaveral in Florida. Wind tunnel tests were made in several Langley tunnels including the Unitary Plan Wind Tunnel, the 8-foot High-Temperature Tunnel and the 9x6-Foot Thermal Structures Tunnel.

Procedures for use in transforming velocity vectors from selenographic system to mean nearest Besselian year